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NASA NLF1015 (nlf1015-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NASA NLF1015 (nlf1015-il)
Reynolds number: 500,000
Max Cl/Cd: 130.62 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nlf1015-il-500000.txt
Download as CSV file: xf-nlf1015-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA  NLF1015                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0143   0.08684   0.08442  -0.1317   0.9402   0.0271
 -11.500  -0.0092   0.08119   0.07876  -0.1361   0.9384   0.0273
 -11.250  -0.0112   0.07403   0.07161  -0.1399   0.9368   0.0280
 -11.000   0.0082   0.07152   0.06907  -0.1424   0.9334   0.0288
 -10.750   0.0230   0.06793   0.06545  -0.1458   0.9294   0.0297
 -10.500  -0.1098   0.07343   0.07097  -0.1430   0.9392   0.0277
 -10.250  -0.0945   0.06953   0.06705  -0.1478   0.9366   0.0283
 -10.000  -0.0757   0.06663   0.06413  -0.1522   0.9313   0.0290
  -9.750  -0.0578   0.05999   0.05745  -0.1622   0.9266   0.0298
  -9.500  -0.0718   0.04603   0.04317  -0.1828   0.9127   0.0299
  -9.250  -0.0752   0.04230   0.03924  -0.1869   0.8987   0.0309
  -9.000  -0.0871   0.03975   0.03647  -0.1866   0.8854   0.0315
  -8.750  -0.0919   0.03711   0.03355  -0.1861   0.8757   0.0327
  -8.500  -0.0895   0.03803   0.03399  -0.1839   0.8664   0.0349
  -8.250  -0.1018   0.03152   0.02725  -0.1829   0.8588   0.0365
  -8.000  -0.0850   0.02994   0.02563  -0.1826   0.8535   0.0374
  -7.750  -0.0864   0.02172   0.01607  -0.1789   0.8476   0.0215
  -7.500  -0.0674   0.01978   0.01402  -0.1779   0.8430   0.0207
  -7.250  -0.0461   0.01812   0.01216  -0.1773   0.8390   0.0203
  -7.000  -0.0210   0.01692   0.01076  -0.1773   0.8357   0.0203
  -6.750   0.0023   0.01600   0.00972  -0.1769   0.8323   0.0204
  -6.500   0.0248   0.01530   0.00894  -0.1762   0.8285   0.0208
  -6.250   0.0489   0.01463   0.00819  -0.1759   0.8250   0.0210
  -6.000   0.0748   0.01409   0.00756  -0.1759   0.8219   0.0212
  -5.750   0.0999   0.01328   0.00667  -0.1761   0.8189   0.0218
  -5.500   0.1222   0.01266   0.00604  -0.1756   0.8157   0.0229
  -5.250   0.1477   0.01227   0.00563  -0.1757   0.8126   0.0242
  -5.000   0.1749   0.01190   0.00520  -0.1760   0.8099   0.0254
  -4.750   0.2034   0.01159   0.00481  -0.1766   0.8074   0.0267
  -4.500   0.2334   0.01126   0.00442  -0.1775   0.8052   0.0301
  -4.250   0.2599   0.01097   0.00416  -0.1776   0.8025   0.0393
  -4.000   0.2869   0.01021   0.00385  -0.1785   0.7997   0.1435
  -3.750   0.3162   0.00962   0.00365  -0.1798   0.7971   0.2565
  -3.500   0.3476   0.00900   0.00346  -0.1816   0.7949   0.3903
  -3.250   0.3797   0.00855   0.00343  -0.1833   0.7929   0.5288
  -3.000   0.4105   0.00859   0.00353  -0.1841   0.7910   0.5844
  -2.750   0.4398   0.00870   0.00364  -0.1846   0.7889   0.6133
  -2.500   0.4669   0.00882   0.00376  -0.1845   0.7865   0.6358
  -2.250   0.4947   0.00895   0.00387  -0.1846   0.7841   0.6510
  -2.000   0.5227   0.00903   0.00395  -0.1847   0.7819   0.6596
  -1.750   0.5520   0.00912   0.00400  -0.1851   0.7799   0.6683
  -1.500   0.5812   0.00921   0.00407  -0.1855   0.7780   0.6757
  -1.250   0.6117   0.00932   0.00410  -0.1863   0.7761   0.6827
  -1.000   0.6396   0.00943   0.00423  -0.1864   0.7742   0.6883
  -0.750   0.6662   0.00952   0.00432  -0.1864   0.7720   0.6949
  -0.500   0.6931   0.00959   0.00440  -0.1864   0.7696   0.7003
  -0.250   0.7206   0.00967   0.00450  -0.1864   0.7673   0.7055
   0.000   0.7499   0.00975   0.00455  -0.1870   0.7652   0.7112
   0.250   0.7792   0.00980   0.00459  -0.1875   0.7632   0.7153
   0.500   0.8091   0.00988   0.00467  -0.1881   0.7612   0.7192
   0.750   0.8367   0.00999   0.00478  -0.1883   0.7589   0.7236
   1.000   0.8628   0.01005   0.00486  -0.1882   0.7560   0.7278
   1.250   0.8894   0.01007   0.00492  -0.1881   0.7530   0.7308
   1.500   0.9177   0.01009   0.00496  -0.1884   0.7501   0.7336
   1.750   0.9480   0.01012   0.00497  -0.1891   0.7473   0.7367
   2.000   0.9770   0.01020   0.00505  -0.1896   0.7443   0.7400
   2.250   1.0016   0.01024   0.00512  -0.1891   0.7404   0.7432
   2.500   1.0282   0.01023   0.00515  -0.1891   0.7366   0.7459
   2.750   1.0575   0.01022   0.00516  -0.1895   0.7330   0.7487
   3.000   1.0863   0.01028   0.00523  -0.1899   0.7295   0.7516
   3.250   1.1093   0.01030   0.00532  -0.1891   0.7251   0.7550
   3.500   1.1367   0.01031   0.00534  -0.1892   0.7206   0.7586
   3.750   1.1663   0.01030   0.00534  -0.1897   0.7164   0.7615
   4.000   1.1882   0.01032   0.00546  -0.1886   0.7112   0.7646
   4.250   1.2131   0.01032   0.00550  -0.1882   0.7058   0.7681
   4.500   1.2428   0.01034   0.00552  -0.1887   0.7010   0.7718
   4.750   1.2624   0.01036   0.00564  -0.1872   0.6947   0.7755
   5.000   1.2864   0.01034   0.00567  -0.1865   0.6884   0.7791
   5.250   1.3078   0.01037   0.00577  -0.1853   0.6814   0.7833
   5.500   1.3294   0.01037   0.00581  -0.1841   0.6729   0.7878
   5.750   1.3449   0.01038   0.00589  -0.1815   0.6615   0.7919
   6.000   1.3584   0.01040   0.00596  -0.1786   0.6471   0.7964
   6.250   1.3658   0.01048   0.00602  -0.1743   0.6277   0.8020
   6.500   1.3691   0.01073   0.00621  -0.1693   0.5981   0.8075
   6.750   1.3689   0.01124   0.00659  -0.1638   0.5577   0.8138
   7.000   1.3665   0.01202   0.00718  -0.1582   0.5170   0.8208
   7.250   1.3617   0.01298   0.00798  -0.1523   0.4771   0.8276
   7.500   1.3567   0.01413   0.00894  -0.1467   0.4361   0.8356
   7.750   1.3520   0.01535   0.01001  -0.1414   0.3965   0.8435
   8.000   1.3476   0.01672   0.01121  -0.1365   0.3573   0.8525
   8.250   1.3448   0.01813   0.01247  -0.1321   0.3186   0.8628
   8.500   1.3424   0.01959   0.01378  -0.1279   0.2818   0.8743
   8.750   1.3413   0.02105   0.01512  -0.1240   0.2461   0.8884
   9.000   1.3388   0.02257   0.01650  -0.1201   0.2113   0.9078
   9.250   1.3332   0.02379   0.01765  -0.1154   0.1811   1.0000
   9.500   1.3362   0.02563   0.01926  -0.1131   0.1431   1.0000
   9.750   1.3403   0.02740   0.02083  -0.1109   0.1115   1.0000
  10.000   1.3428   0.02934   0.02255  -0.1086   0.0781   1.0000
  10.250   1.3416   0.03162   0.02458  -0.1061   0.0430   1.0000
  10.500   1.3418   0.03389   0.02666  -0.1037   0.0203   1.0000
  10.750   1.3500   0.03557   0.02835  -0.1021   0.0158   1.0000
  11.000   1.3609   0.03703   0.02987  -0.1009   0.0143   1.0000
  11.250   1.3715   0.03853   0.03144  -0.0997   0.0134   1.0000
  11.500   1.3809   0.04017   0.03314  -0.0985   0.0126   1.0000
  11.750   1.3877   0.04209   0.03512  -0.0971   0.0120   1.0000
  12.000   1.3920   0.04429   0.03742  -0.0956   0.0115   1.0000
  12.250   1.4011   0.04605   0.03926  -0.0945   0.0112   1.0000
  12.500   1.4087   0.04798   0.04129  -0.0934   0.0108   1.0000
  12.750   1.4155   0.05005   0.04344  -0.0924   0.0105   1.0000
  13.000   1.4210   0.05229   0.04577  -0.0914   0.0102   1.0000
  13.250   1.4260   0.05462   0.04819  -0.0904   0.0100   1.0000
  13.500   1.4299   0.05713   0.05078  -0.0894   0.0098   1.0000
  13.750   1.4336   0.05971   0.05344  -0.0886   0.0096   1.0000
  14.000   1.4366   0.06242   0.05624  -0.0878   0.0094   1.0000
  14.250   1.4387   0.06529   0.05920  -0.0870   0.0093   1.0000
  14.500   1.4406   0.06825   0.06224  -0.0864   0.0091   1.0000
  14.750   1.4415   0.07135   0.06545  -0.0858   0.0090   1.0000
  15.000   1.4426   0.07451   0.06869  -0.0852   0.0089   1.0000
  15.250   1.4440   0.07765   0.07193  -0.0847   0.0088   1.0000
  15.500   1.4473   0.08059   0.07497  -0.0840   0.0087   1.0000
  15.750   1.4522   0.08335   0.07784  -0.0835   0.0086   1.0000
  16.000   1.4566   0.08625   0.08086  -0.0834   0.0085   1.0000
  16.250   1.4604   0.08926   0.08400  -0.0834   0.0085   1.0000
  16.500   1.4635   0.09239   0.08728  -0.0834   0.0084   1.0000
  16.750   1.4657   0.09571   0.09074  -0.0836   0.0084   1.0000
  17.000   1.4669   0.09917   0.09435  -0.0838   0.0084   1.0000
  17.250   1.4663   0.10296   0.09831  -0.0843   0.0084   1.0000
  17.500   1.4645   0.10697   0.10250  -0.0850   0.0083   1.0000
  17.750   1.4616   0.11119   0.10690  -0.0859   0.0084   1.0000
  18.000   1.4569   0.11576   0.11164  -0.0871   0.0084   1.0000
  18.250   1.4498   0.12079   0.11687  -0.0888   0.0084   1.0000
  18.500   1.4416   0.12611   0.12237  -0.0909   0.0084   1.0000
  18.750   1.4322   0.13175   0.12819  -0.0934   0.0084   1.0000
  19.000   1.4216   0.13774   0.13437  -0.0964   0.0084   1.0000
  19.250   1.4107   0.14394   0.14075  -0.0998   0.0084   1.0000
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